Topic
Afterburner
About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.
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31 Jul 2011
TL;DR: The Scimitar engine is the hydrogen-fueled propulsive plant of the airplane A2, a concept proposed by Reaction Engines Ltd., partner company in the project Long-Term Advanced Propulsion Concepts and Technologies II (LAPCAT).
Abstract: The Scimitar engine is the hydrogen-fueled propulsive plant of the airplane A2, a concept proposed by Reaction Engines Ltd., partner company in the project Long-Term Advanced Propulsion Concepts and Technologies II (LAPCAT). The Scimitar features a variable cycle engine that combines a turbofan based cycle with an air-turbo-rocket cycle Fig. 1. The turbofan based cycle operates from take-o to Mach 2.5. It is augmented with an afterburner during the acceleration phase only, having the capability of maintaining a "dry" subsonic cruise regime at Mach 0.9. Between Mach 2.5 and Mach 5 the engine have the dual operation of an air-turbo-rocket with a ramjet burner in the bypass. At Mach 5 the vehicle cruises and the cycle is that of a gas generator air-turbo-rocket engine.
9 citations
Patent•
26 Aug 1974
TL;DR: In this article, the authors describe a propulsion unit made up of an outer burner wall that is generally polyhedronical and/or generally conical at its forward component and generally cylindrical at its rearward end, a combustion shell concentrically disposed inside the inner burner wall and defining an annular space for combustion between them.
Abstract: The specification discloses a propulsion unit made up of an outer burner wall that is generally polyhedronical and/or generally conical at its forward component and generally cylindrical at its rearward end, a combustion shell concentrically disposed inside the outer burner wall and defining an annular space for combustion between them. Fuel lines are connected to feed fuel directly to the annular space. A cylindrical shell is supported around the burner wall, open at the front, to gather ram air. Flutter valves close intermittently in accordance with the spark plug sparks and/or predetermined combustion rates. The pulse jet section fuel nozzles admit fuel to the forward continuous annular generally conical combustion space forming the pulse jet section and afterburner fuel nozzles admit fuel to the more central and rearward portions of said generally annular combustion space which form the first stages of the afterburner section. An electric motor moves the inner shell relative to the outer shell to change the size of the space between them, thus regulating combustion chamber volume as required. This makes it possible to use the propulsion unit at low speeds as well as high speeds and makes possible lower as well as higher predetermined combustion rates. The combination of shells results in a multi-stage pulse jet unit and a multi-stage afterburner unit. The two units operate to provide a highly efficient jet engine, capable at its higher propulsive effort of becoming a self-propelled ram jet engine.
9 citations
TL;DR: In this article, the performance and thermodynamic parameters of the engine under different operating modes are examined and compared according to the built mathematical models, and the simulation results show that the effects of operating modes on the engine are remarkably different from that on the traditional SOFC gas turbine hybrid systems for electricity generation.
9 citations
Patent•
19 May 2004
TL;DR: In this paper, a retractable afterburner cover for a jet engine has been proposed, which is affixed by a plurality of moveable support arms to the outer surface of the engine.
Abstract: The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable. During operation of the afterburner shroud, the afterburner shroud is extended rearward toward the exhaust of the jet engine. A storage tank provides liquid oxygen through the support arms to a mixing ring located within the afterburner shroud. The mixing ring mixes the liquid oxygen and fuel to form a combustible mixture. The combustible mixture is injected into the exhaust wherein the mixture is ignited. The ignited mixture provides additional thrust for the jet engine.
8 citations
Patent•
21 Sep 1978
TL;DR: In this article, a fuel distribution device for high velocity gase flow is proposed, consisting of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices and arranged to introduce fuel into the flow.
Abstract: The invention concerns a fuel distribution device in a high velocity gase flow. The device consists of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices and arranged to introduce fuel into the flow. The orifices in the manifold located downstream with respect to the direction of the flow of gases, are arranged on the face turned upstream of the manifold, in a circular row coaxial with it. It is the object of the invention to reduce the drag induced in the flow by the devices presently in use, while improving the distribution of the fuel; it finds particularly advantageous applications in the afterburner ducts of gas turbine engines.
8 citations